Integrated nacelle inlet and metallic fan containment case

Patent metadata

Field	Value
Publication number	US-9534505-B2
Application number	US-201213555303-A
Country	US
Kind code	B2
Filing date	Jul 23, 2012
Priority date	Jul 23, 2012
Publication date	Jan 3, 2017
Grant date	Jan 3, 2017

Abstract

A fan nacelle includes a metallic fan containment case. A nacelle inlet is secured to the metallic fan containment case by permanent fastening elements. A gas turbine engine includes a metallic fan containment case. A core engine has a static engine structure housing a compressor section, a combustor section and a turbine section. The core engine is configured to receive core airflow. A fan is arranged within the metallic fan containment case. The fan is coupled to the core engine and is arranged in a bypass flowpath provided between the core engine and the metallic fan containment case. A nacelle inlet is secured to the metallic fan containment case by permanent fastening elements.

First claim

What is claimed is:

1. A fan nacelle comprising:
a metallic fan containment case includes first and second flanges;
a nacelle inlet secured to the metallic fan containment case by permanent fastening elements, wherein the nacelle inlet has an arcuate hollow cross-section, an apex of the arcuate cross-section provides a forward-most portion of the fan nacelle, the nacelle inlet is configured to provide a smooth entry for fluid into the fan nacelle, and wherein the nacelle inlet includes a first wall substantially perpendicular to a second wall, the first and second walls respectively secured to the first and second flanges by the permanent fastening elements; and
a rub strip supported by the fan containment case and configured to provide a seal relative to a fan.

2. The fan nacelle according to claim 1 , wherein the nacelle inlet is a metallic structure.

3. The fan nacelle according to claim 1 , wherein the nacelle inlet is a composite structure.

4. The fan nacelle according to claim 1 , wherein the permanent fastening elements is an adhesive.

5. The fan nacelle according to claim 1 , wherein the permanent fastening elements is a weld.

6. The fan nacelle according to claim 1 , wherein the permanent fastening elements is a rivet.

7. The fan nacelle according to claim 1 , wherein the nacelle inlet is C-shaped.

8. The fan nacelle according to claim 1 , the metallic fan containment case having a mount at an aft end configured to be secured to flow exit guide vanes.

9. The fan nacelle according to claim 1 , wherein the first and second flanges are positioned at a forward end of the metallic fan containment case.

10. The fan nacelle according to claim 1 , wherein the nacelle inlet includes an annular cavity between the first and second walls.

11. The fan nacelle according to claim 1 , wherein the nacelle inlet includes a reinforcing member secured between the first and second walls.

12. A gas turbine engine comprising:
a metallic fan containment case;
a core engine having a static engine structure housing a compressor section, a combustor section and a turbine section, the core engine configured to receive core airflow;
a fan arranged within the metallic fan containment case, the fan is coupled to the core engine and is arranged in a bypass flowpath provided between the core engine and the metallic fan containment case; and
a fan nacelle surrounds the metallic fan containment case and provides an outer flow path surface of the bypass flowpath, wherein the metallic fan containment case includes first and second flanges forward of a fan blade, and the fan nacelle includes a nacelle inlet having first and second walls respectively secured to the first and second flanges by permanent fastening elements, wherein the nacelle inlet is a metallic structure that has an arcuate hollow cross-section, an apex of the arcuate cross-section provides a forward-most portion of the fan nacelle, the nacelle inlet is configured to provide a smooth entry for fluid into the bypass flowpath.

13. The gas turbine engine according to claim 12 , wherein the permanent fastening elements is an adhesive.

14. The gas turbine engine according to claim 12 , wherein the permanent fastening elements is a weld.

15. The gas turbine engine according to claim 12 , wherein the permanent fastening elements is a rivet.

16. The gas turbine engine according to claim 12 , wherein the fan containment case supports a rub strip configured to provide a seal relative to the fan.

17. The gas turbine engine according to claim 12 , wherein the nacelle inlet is C-shaped.

18. The gas turbine engine according to claim 12 , wherein the first wall is substantially perpendicular to the second wall.

19. The gas turbine engine according to claim 12 , the metallic fan containment case having a mount at an aft end secured to flow exit guide vanes.

20. The gas turbine engine according to claim 12 , wherein the nacelle inlet includes a reinforcing member secured between the first and second walls.

21. A gas turbine engine comprising:
a metallic fan containment case including first and second flanges at a forward end of the metallic fan containment case;
a core engine having a static engine structure housing a compressor section, a combustor section and a turbine section, the core engine configured to receive core airflow;
a fan arranged within the metallic fan containment case, the fan is coupled to the core engine and is arranged in a bypass flowpath provided between the core engine and the metallic fan containment case; and
a nacelle inlet having first and second walls secured to the first and second flanges of the metallic fan containment case by permanent fastening elements, the nacelle inlet is configured to provide a smooth entry for fluid into the fan nacelle, and wherein the nacelle inlet is a composite structure.

22. The gas turbine engine according to claim 21 , wherein the nacelle inlet is C-shaped.

23. The gas turbine engine according to claim 21 , wherein the first wall is substantially perpendicular to the second wall.

24. The gas turbine engine according to claim 21 , the metallic fan containment case having a mount at an aft end secured to flow exit guide vanes.

25. The gas turbine engine according to claim 21 , wherein the nacelle inlet includes a reinforcing member secured between the first and second walls.

26. The gas turbine engine according to claim 21 , wherein the first and second flanges are forward of a fan blade.

Assignees

• Lucas James L
• United Technologies Corp

Inventors

• Lucas James L

Classifications

• F01D21/045 Primary

  special arrangements in stators or in rotors dealing with breaking-off of part of rotor · CPC title

• B64D33/02

  of combustion air intakes · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title